Figure 2 its attitude history, as indicated for example, by the second quaternion of an Euler parameter attitude description. Figure 3 shows the time-history of the third-assumed mode of vibration of the rocket. Figure 4 shows the mass depletion rate, bringing out the crucial variable mass character of the rocket. The results show the generality of the mathematical equations provided in this paper. The formulation itself should be useful for nonlinear control design of the flight of a rocket that can bend in flight.
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